US7055307B2 - Vectorable nozzle with sideways pivotable ramp - Google Patents

Vectorable nozzle with sideways pivotable ramp Download PDF

Info

Publication number
US7055307B2
US7055307B2 US10/930,881 US93088104A US7055307B2 US 7055307 B2 US7055307 B2 US 7055307B2 US 93088104 A US93088104 A US 93088104A US 7055307 B2 US7055307 B2 US 7055307B2
Authority
US
United States
Prior art keywords
pivotable
wall
nozzle
extending
ramp structure
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active, expires
Application number
US10/930,881
Other versions
US20060042230A1 (en
Inventor
Edward James Wehner
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US10/930,881 priority Critical patent/US7055307B2/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WEHNER, EDWARD JAMES
Priority to ES05254714T priority patent/ES2420760T3/en
Priority to EP05254714.8A priority patent/EP1630399B1/en
Publication of US20060042230A1 publication Critical patent/US20060042230A1/en
Application granted granted Critical
Publication of US7055307B2 publication Critical patent/US7055307B2/en
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F02K1/006—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector within one plane only
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation

Definitions

  • the invention relates to aircraft gas turbine engine two dimensional vectoring nozzles and, more particularly, for such nozzles designed to shift center of nozzle exhaust flow sideways to effect vectoring.
  • Aircraft designers and particularly those designing high speed highly maneuverable military aircraft are constantly seeking better ways for controlling the aircraft and increasing its maneuverability in flight. These are needed for anti-aircraft missile avoidance and other combat maneuvers. Additionally, aircraft designers are trying to improve short take off and landing capabilities of aircraft. Exhaust systems, particularly for modern, high speed, military aircraft, have been adapted to provide a high degree of maneuverability over a wide variety of flight conditions including altitude, speed and Mach number while maintaining cruise efficiency.
  • Aircraft maneuverability may be provided by aircraft control surfaces such as wing flaps or ailerons or vertical fins or rudders. Aircraft control surfaces, however, are somewhat limited in their effectiveness because of large differences in operational flight conditions such as air speed. Aircraft control surfaces also increase an aircraft's radar signature making it more vulnerable to anti-aircraft fire and missile. Thrust vectoring nozzles, though often more complicated, are more effective because they allow large thrust loads to be quickly applied in the pitch and yaw direction of the aircraft, thereby, providing the aircraft with enhanced maneuverability which is relatively independent of air speed. Thrust vectoring nozzles are complex, heavy, and expensive. Other thrust vectoring methods include use of nozzle internal fluidic injection and/or mechanical flow diversion devices to skew the thrust. These thrust vectoring methods are effective but may be complex, heavy, costly and/or marginally effective.
  • a vectorable nozzle for use with an aircraft gas turbine engine includes a longitudinally extending upper fixed wall spaced upwardly and aftwardly of a longitudinally extending lower fixed wall and an aftwardly swept fixed ramp extending between the upper and lower fixed walls.
  • the upper and lower fixed walls and the fixed ramp extend transversely between first and second fixed sidewalls.
  • An outer nozzle wall is spaced apart from the upper and lower fixed walls and extends transversely between first and second fixed sidewalls.
  • a nozzle flowpath is defined between the upper and lower fixed walls and the outer nozzle wall and the first and second fixed sidewalls.
  • a sideways pivotable ramp structure pivotally connected to the lower fixed wall and pivotable between the sidewalls includes a longitudinally extending upper pivotable wall spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall and an aftwardly swept pivotable ramp extending between the upper and lower pivotable walls.
  • the upper pivotable wall includes a widthwise aftwardly tapered section which may have an isosceles triangular planform area including side edges extending equi-angularly aftwardly from a base line between the tapered section and a non-tapered section of the upper pivotable wall. Taper angles between the side edges and the base line may be sized for allowing the side edges to substantially abut respective ones of the sidewalls when the pivotable ramp structure is pivoted sideways.
  • a fin may be attached to the pivotable ramp structure along at least longitudinally extending first and second portions of the lower pivotable wall and the pivotable ramp respectively, and may extend longitudinally over a pivot point where the ramp structure is pivotally connected to the lower fixed wall.
  • a more particular embodiment of the vectorable nozzle includes a widthwise aftwardly tapered section of the upper pivotable wall and a base line between the tapered section and a non-tapered section of the upper pivotable wall.
  • a throat extends substantially downward across the nozzle flowpath from the outer nozzle wall to the ramp structure, and the tapered and non-tapered sections are contoured so that the throat extends widthwise substantially along the base line during vectored and unvectored operation of the nozzle.
  • Another more particular embodiment of the vectorable nozzle includes an upper triangular surface of the upper fixed wall bounding nozzle flowpath and at least a portion of the upper triangular surface extending aftwardly of the first and second fixed sidewalls to an apex of the triangular surface.
  • FIG. 1 is a partially cut-away perspective view illustration of a vectorable nozzle with a sideways pivotable ramp.
  • FIG. 2 is a cross-section top looking down view illustration of the vectorable nozzle in FIG. 1 .
  • FIG. 3 is a cross-section top looking down view illustration of the vectorable nozzle in FIG. 1 with throat locations illustrated therein.
  • FIG. 4 is a cross-section forward looking aft view illustration of the vectorable nozzle in FIG. 1 with the pivotable ramp not pivoted.
  • FIG. 5 is a cross-section forward looking aft view illustration of the vectorable nozzle in FIG. 1 with the pivotable ramp fully pivoted.
  • FIG. 6 is a cross-section side view illustration of the vectorable nozzle in FIG. 1 .
  • FIGS. 1 and 2 Illustrated in FIGS. 1 and 2 is an exemplary embodiment of a vectorable nozzle 12 designed to vector exhaust flow 15 sideways.
  • the vectorable nozzle 12 includes an outer casing 10 which is connected to an aft end of an aircraft gas turbine engine (not shown) by a transition duct 13 .
  • the transition duct 13 converts the exhaust flow 15 from one with a circular cross-section or axisymmetric exhaust flow 15 to one having a rectangular cross-section or two-dimensional (2D) exhaust flow 15 .
  • 2D two-dimensional
  • the vectorable nozzle 12 includes a longitudinally extending upper fixed wall 14 spaced upwardly and aftwardly of a longitudinally extending lower fixed wall 16 and an aftwardly swept fixed ramp 18 extending between the upper and lower fixed walls 14 and 16 .
  • the upper and lower fixed walls 14 and 16 and the fixed ramp 18 extend transversely between first and second fixed sidewalls 20 and 22 .
  • An outer nozzle wall 23 is spaced apart from the upper and lower fixed walls 14 and 16 and extends transversely between first and second fixed sidewalls 20 and 22 .
  • a nozzle flowpath 40 is defined between the upper and lower fixed walls 14 and 16 and the outer nozzle wall 23 and the first and second fixed sidewalls 20 and 22 .
  • a sideways pivotable ramp structure 24 is pivotally connected to the lower fixed wall 16 and is sideways pivotable between the sidewalls 20 and 22 .
  • the pivotable ramp structure 24 includes a longitudinally extending upper pivotable wall 34 spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall 36 and an aftwardly swept pivotable ramp 38 extending between the upper and lower pivotable walls 34 and 36 .
  • the sideways pivotable ramp structure 24 may also be described as being sideways pivotable within the outer casing 10 , particularly, if there are no clearly definable or identifiable sidewalls 20 and 22 such as in the case of smoothed curved continuous outer nozzle wall 23 extending around to the upper and lower fixed walls 14 and 16 .
  • the upper pivotable wall 34 includes a widthwise aftwardly tapered section 44 illustrated as having an isosceles triangular planform area 46 .
  • the aftwardly tapered section 44 includes side edges 48 extending equi-angularly aftwardly from a base line 50 between the tapered section 44 and a non-tapered section 54 (illustrated as being rectangular) of the upper pivotable wall 34 .
  • Taper angles 58 between the side edges 48 and the base line 50 are sized for allowing the side edges 48 to substantially abut respective ones of the sidewalls 20 and 22 when the pivotable ramp structure 24 is pivoted sideways.
  • An upper triangular surface 80 of the upper fixed wall 14 bounds nozzle flowpath 40 . At least a portion of the upper triangular surface 80 extends aftwardly of the first and second fixed sidewalls 20 and 22 to an apex 82 of the triangular surface 80 .
  • the upper triangular surface 80 extending aftwardly past the first and second fixed sidewalls 20 and 22 and the outer casing 10 allows vectoring of the exhaust flow 15 by allowing it to expand in the left and right sideway directions LS and RS respectively aftward of the outer casing 10 .
  • the fin 62 extends longitudinally over a pivot point 72 (illustrated in FIG. 6 ).
  • the ramp structure 24 is pivotally connected to the lower fixed wall 16 at the pivot point 72 .
  • a throat A 8 illustrated in FIGS. 3 and 6 , of the nozzle 12 extends substantially downward across the nozzle flowpath 40 from the outer nozzle wall 23 to the ramp structure 24 .
  • a center plane 134 passes through the fin 62 when the ramp structure 24 is in the non-pivoted position 126 .
  • the tapered and non-tapered sections 44 and 54 are contoured so that the throat A 8 extends widthwise substantially along the base line 50 during vectored and unvectored operation of the nozzle 12 .
  • the ramp structure 24 is pivoted fully or partially sideways.
  • FIG. 2 illustrates the ramp structure 24 in a fully sideways pivoted position 124 illustrated in phantom line as compared to a non-pivoted position 126 .
  • FIG. 3 illustrates the exhaust flow 15 vectored sideways forming a sideways vectored nozzle exit flow 90 as compared to an unvectored nozzle exit flow 92 corresponding to the ramp structure 24 in a fully sideways pivoted position 124 and the non-pivoted position 126 , respectively.
  • the throat A 8 has a substantially symmetric shape 130 about the center plane 134 when the ramp structure 24 is in the non-pivoted position 126 and asymmetric shape 132 about the center plane 134 when the ramp structure 24 is in a vectored position illustrated by the fully sideways pivoted position 124 .
  • the vectorable nozzle 12 vectors the thrust by simultaneously shifting the exhaust flow 15 advantageously sideways for vectoring and skewing the exhaust flow 15 flow at the throat A 8 .
  • FIG. 4 illustrates a center 140 of the exhaust flow 15 centered sideways when the ramp structure 24 is in the non-pivoted position 126 and the thrust and exhaust flow 15 are not vectored.
  • FIG. 5 illustrates the center 140 of the exhaust flow 15 shifted sideways when the ramp structure 24 is in the fully sideways pivoted position 124 and the thrust and exhaust flow 15 are vectored.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Catching Or Destruction (AREA)
  • Supports For Pipes And Cables (AREA)
  • Supercharger (AREA)

Abstract

A vectorable nozzle includes a longitudinally extending upper fixed wall spaced upwardly and aftwardly of a longitudinally extending lower fixed wall and an aftwardly swept fixed ramp extending between the upper and lower fixed walls. The upper and lower fixed walls and the fixed ramp extend transversely between first and second fixed sidewalls. An outer nozzle wall is spaced apart from the upper and lower fixed walls and extends transversely between first and second fixed sidewalls. A nozzle flowpath is defined between the upper and lower fixed walls and the outer nozzle wall and the first and second fixed sidewalls. A sideways pivotable ramp structure pivotally connected to the lower fixed wall and pivotable between the sidewalls includes a longitudinally extending upper pivotable wall spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall and an aftwardly swept pivotable ramp extending between the upper and lower pivotable walls.

Description

BACKGROUND OF THE INVENTION Field of the Invention
The invention relates to aircraft gas turbine engine two dimensional vectoring nozzles and, more particularly, for such nozzles designed to shift center of nozzle exhaust flow sideways to effect vectoring.
Aircraft designers and particularly those designing high speed highly maneuverable military aircraft are constantly seeking better ways for controlling the aircraft and increasing its maneuverability in flight. These are needed for anti-aircraft missile avoidance and other combat maneuvers. Additionally, aircraft designers are trying to improve short take off and landing capabilities of aircraft. Exhaust systems, particularly for modern, high speed, military aircraft, have been adapted to provide a high degree of maneuverability over a wide variety of flight conditions including altitude, speed and Mach number while maintaining cruise efficiency.
Aircraft maneuverability may be provided by aircraft control surfaces such as wing flaps or ailerons or vertical fins or rudders. Aircraft control surfaces, however, are somewhat limited in their effectiveness because of large differences in operational flight conditions such as air speed. Aircraft control surfaces also increase an aircraft's radar signature making it more vulnerable to anti-aircraft fire and missile. Thrust vectoring nozzles, though often more complicated, are more effective because they allow large thrust loads to be quickly applied in the pitch and yaw direction of the aircraft, thereby, providing the aircraft with enhanced maneuverability which is relatively independent of air speed. Thrust vectoring nozzles are complex, heavy, and expensive. Other thrust vectoring methods include use of nozzle internal fluidic injection and/or mechanical flow diversion devices to skew the thrust. These thrust vectoring methods are effective but may be complex, heavy, costly and/or marginally effective.
It is, thus, highly desirable to provide an aircraft gas turbine engine with a thrust vectoring nozzle that is not complex, nor heavy, nor expensive, and yet, very effective for thrust vectoring.
SUMMARY OF THE INVENTION
A vectorable nozzle for use with an aircraft gas turbine engine includes a longitudinally extending upper fixed wall spaced upwardly and aftwardly of a longitudinally extending lower fixed wall and an aftwardly swept fixed ramp extending between the upper and lower fixed walls. The upper and lower fixed walls and the fixed ramp extend transversely between first and second fixed sidewalls. An outer nozzle wall is spaced apart from the upper and lower fixed walls and extends transversely between first and second fixed sidewalls. A nozzle flowpath is defined between the upper and lower fixed walls and the outer nozzle wall and the first and second fixed sidewalls. A sideways pivotable ramp structure pivotally connected to the lower fixed wall and pivotable between the sidewalls includes a longitudinally extending upper pivotable wall spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall and an aftwardly swept pivotable ramp extending between the upper and lower pivotable walls.
In an exemplary embodiment of the vectorable nozzle, the upper pivotable wall includes a widthwise aftwardly tapered section which may have an isosceles triangular planform area including side edges extending equi-angularly aftwardly from a base line between the tapered section and a non-tapered section of the upper pivotable wall. Taper angles between the side edges and the base line may be sized for allowing the side edges to substantially abut respective ones of the sidewalls when the pivotable ramp structure is pivoted sideways.
A fin may be attached to the pivotable ramp structure along at least longitudinally extending first and second portions of the lower pivotable wall and the pivotable ramp respectively, and may extend longitudinally over a pivot point where the ramp structure is pivotally connected to the lower fixed wall.
A more particular embodiment of the vectorable nozzle includes a widthwise aftwardly tapered section of the upper pivotable wall and a base line between the tapered section and a non-tapered section of the upper pivotable wall. A throat extends substantially downward across the nozzle flowpath from the outer nozzle wall to the ramp structure, and the tapered and non-tapered sections are contoured so that the throat extends widthwise substantially along the base line during vectored and unvectored operation of the nozzle.
Another more particular embodiment of the vectorable nozzle includes an upper triangular surface of the upper fixed wall bounding nozzle flowpath and at least a portion of the upper triangular surface extending aftwardly of the first and second fixed sidewalls to an apex of the triangular surface.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a partially cut-away perspective view illustration of a vectorable nozzle with a sideways pivotable ramp.
FIG. 2 is a cross-section top looking down view illustration of the vectorable nozzle in FIG. 1.
FIG. 3 is a cross-section top looking down view illustration of the vectorable nozzle in FIG. 1 with throat locations illustrated therein.
FIG. 4 is a cross-section forward looking aft view illustration of the vectorable nozzle in FIG. 1 with the pivotable ramp not pivoted.
FIG. 5 is a cross-section forward looking aft view illustration of the vectorable nozzle in FIG. 1 with the pivotable ramp fully pivoted.
FIG. 6 is a cross-section side view illustration of the vectorable nozzle in FIG. 1.
 DETAILED DESCRIPTION OF THE INVENTION
Illustrated in FIGS. 1 and 2 is an exemplary embodiment of a vectorable nozzle 12 designed to vector exhaust flow 15 sideways. The vectorable nozzle 12 includes an outer casing 10 which is connected to an aft end of an aircraft gas turbine engine (not shown) by a transition duct 13. The transition duct 13 converts the exhaust flow 15 from one with a circular cross-section or axisymmetric exhaust flow 15 to one having a rectangular cross-section or two-dimensional (2D) exhaust flow 15. At this point, it is important to define the conventions used to describe the directions and frame of references for the flow, the movement of various nozzle elements. Forward and aft directions F and A are illustrated in FIG. 1 by respective arrows. Left and right sideway LS and RS directions are illustrated in FIG. 1 by respective arrows from a frame of reference forward looking aft. Upper and lower directions U and L are illustrated in FIG. 1 by respective arrows. Upper and lower elements and right and left elements are used only for describing the nozzle within the illustrated reference frame.
Referring to FIGS. 1 and 6, the vectorable nozzle 12 includes a longitudinally extending upper fixed wall 14 spaced upwardly and aftwardly of a longitudinally extending lower fixed wall 16 and an aftwardly swept fixed ramp 18 extending between the upper and lower fixed walls 14 and 16. The upper and lower fixed walls 14 and 16 and the fixed ramp 18 extend transversely between first and second fixed sidewalls 20 and 22. An outer nozzle wall 23 is spaced apart from the upper and lower fixed walls 14 and 16 and extends transversely between first and second fixed sidewalls 20 and 22. A nozzle flowpath 40 is defined between the upper and lower fixed walls 14 and 16 and the outer nozzle wall 23 and the first and second fixed sidewalls 20 and 22.
A sideways pivotable ramp structure 24 is pivotally connected to the lower fixed wall 16 and is sideways pivotable between the sidewalls 20 and 22. The pivotable ramp structure 24 includes a longitudinally extending upper pivotable wall 34 spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall 36 and an aftwardly swept pivotable ramp 38 extending between the upper and lower pivotable walls 34 and 36. The sideways pivotable ramp structure 24 may also be described as being sideways pivotable within the outer casing 10, particularly, if there are no clearly definable or identifiable sidewalls 20 and 22 such as in the case of smoothed curved continuous outer nozzle wall 23 extending around to the upper and lower fixed walls 14 and 16.
The upper pivotable wall 34 includes a widthwise aftwardly tapered section 44 illustrated as having an isosceles triangular planform area 46. The aftwardly tapered section 44 includes side edges 48 extending equi-angularly aftwardly from a base line 50 between the tapered section 44 and a non-tapered section 54 (illustrated as being rectangular) of the upper pivotable wall 34. Taper angles 58 between the side edges 48 and the base line 50 are sized for allowing the side edges 48 to substantially abut respective ones of the sidewalls 20 and 22 when the pivotable ramp structure 24 is pivoted sideways.
An upper triangular surface 80 of the upper fixed wall 14 bounds nozzle flowpath 40. At least a portion of the upper triangular surface 80 extends aftwardly of the first and second fixed sidewalls 20 and 22 to an apex 82 of the triangular surface 80. The upper triangular surface 80 extending aftwardly past the first and second fixed sidewalls 20 and 22 and the outer casing 10 allows vectoring of the exhaust flow 15 by allowing it to expand in the left and right sideway directions LS and RS respectively aftward of the outer casing 10.
A fin 62 attached to the pivotable ramp structure 24 along at least longitudinally extending first and second portions 68 and 70 of the lower pivotable wall 36 and the pivotable ramp 38 respectively provides aerodynamically self-centering the pivotable ramp 38 which is particularly desirable if a failure of an actuation system for pivoting the pivotable ramp should occur. The fin 62 extends longitudinally over a pivot point 72 (illustrated in FIG. 6). The ramp structure 24 is pivotally connected to the lower fixed wall 16 at the pivot point 72.
A throat A8, illustrated in FIGS. 3 and 6, of the nozzle 12 extends substantially downward across the nozzle flowpath 40 from the outer nozzle wall 23 to the ramp structure 24. A center plane 134 passes through the fin 62 when the ramp structure 24 is in the non-pivoted position 126. The tapered and non-tapered sections 44 and 54 are contoured so that the throat A8 extends widthwise substantially along the base line 50 during vectored and unvectored operation of the nozzle 12. During unvectored operation of the nozzle 12, the ramp structure 24 is pivoted fully or partially sideways. FIG. 2 illustrates the ramp structure 24 in a fully sideways pivoted position 124 illustrated in phantom line as compared to a non-pivoted position 126.
FIG. 3 illustrates the exhaust flow 15 vectored sideways forming a sideways vectored nozzle exit flow 90 as compared to an unvectored nozzle exit flow 92 corresponding to the ramp structure 24 in a fully sideways pivoted position 124 and the non-pivoted position 126, respectively. The throat A8 has a substantially symmetric shape 130 about the center plane 134 when the ramp structure 24 is in the non-pivoted position 126 and asymmetric shape 132 about the center plane 134 when the ramp structure 24 is in a vectored position illustrated by the fully sideways pivoted position 124.
The vectorable nozzle 12 vectors the thrust by simultaneously shifting the exhaust flow 15 advantageously sideways for vectoring and skewing the exhaust flow 15 flow at the throat A8. FIG. 4 illustrates a center 140 of the exhaust flow 15 centered sideways when the ramp structure 24 is in the non-pivoted position 126 and the thrust and exhaust flow 15 are not vectored. FIG. 5 illustrates the center 140 of the exhaust flow 15 shifted sideways when the ramp structure 24 is in the fully sideways pivoted position 124 and the thrust and exhaust flow 15 are vectored.
The present invention has been described in an illustrative manner. It is to be understood that the terminology which has been used is intended to be in the nature of words of description rather than of limitation. While there have been described herein, what are considered to be preferred and exemplary embodiments of the present invention, other modifications of the invention shall be apparent to those skilled in the art from the teachings herein and, it is, therefore, desired to be secured in the appended claims all such modifications as fall within the true spirit and scope of the invention.
Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims:

Claims (26)

1. A vectorable nozzle comprising:
a longitudinally extending upper fixed wall spaced upwardly and aftwardly of a longitudinally extending lower fixed wall,
an aftwardly swept fixed ramp extending between the upper and lower fixed walls,
the upper and lower fixed walls and the fixed ramp extending transversely between first and second fixed sidewalls,
an outer nozzle wall spaced apart from the upper and lower fixed walls, extending transversely between first and second fixed sidewalls,
a nozzle flowpath defined between the upper and lower fixed walls and the outer nozzle wall and the first and second fixed sidewalls,
a sideways pivotable ramp structure pivotally connected to the lower fixed wall and pivotable between the sidewalls, and
the pivotable ramp structure including a longitudinally extending upper pivotable wall spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall and an aftwardly swept pivotable ramp extending between the upper and lower pivotable walls.
2. A vectorable nozzle as claimed in claim 1 further comprising the upper pivotable wall including a widthwise aftwardly tapered section.
3. A vectorable nozzle as claimed in claim 2 further comprising the tapered section having an isosceles triangular planform area including side edges extending equi-angularly aftwardly from a base line between the tapered section and a non-tapered section of the upper pivotable wall.
4. A vectorable nozzle as claimed in claim 3 further comprising taper angles between the side edges and the base line and the taper angles sized for allowing the side edges to substantially abut respective ones of the sidewalls when the pivotable ramp structure is pivoted sideways.
5. A vectorable nozzle as claimed in claim 4 further comprising a fin attached to the pivotable ramp structure.
6. A vectorable nozzle as claimed in claim 5 further comprising the fin being attached to the pivotable ramp structure along at least longitudinally extending first and second portions of the lower pivotable wall and the pivotable ramp respectively.
7. A vectorable nozzle as claimed in claim 6 further comprising the fin extending longitudinally over a pivot point where the ramp structure is pivotally connected to the lower fixed wall.
8. A vectorable nozzle as claimed in claim 2 further comprising:
the upper pivotable wall including a widthwise aftwardly tapered section and a base line between the tapered section and a non-tapered section of the upper pivotable wall,
a throat extending substantially downward across the nozzle flowpath from the outer nozzle wall to the ramp structure, and
the tapered and non-tapered sections of the upper pivotable wall being contoured so that the throat extends widthwise substantially along the base line during vectored and unvectored operation of the nozzle.
9. A vectorable nozzle as claimed in claim 8 further comprising the tapered section having an isosceles triangular planform area including side edges extending equi-angularly aftwardly from the base line between the tapered and the non-tapered sections of the upper pivotable wall.
10. A vectorable nozzle as claimed in claim 9 further comprising taper angles between the side edges and the base line and the taper angles sized for allowing the side edges to substantially abut respective ones of the sidewalls when the pivotable ramp structure is pivoted sideways.
11. A vectorable nozzle as claimed in claim 10 further comprising a fin attached to the pivotable ramp structure.
12. A vectorable nozzle as claimed in claim 11 further comprising the fin being attached to the pivotable ramp structure along at least longitudinally extending first and second portions of the lower pivotable wall and the pivotable ramp respectively.
13. A vectorable nozzle as claimed in claim 12 further comprising the fin extending longitudinally over a pivot point where the ramp structure is pivotally connected to the lower fixed wall.
14. A vectorable nozzle as claimed in claim 1 further comprising an upper triangular surface of the upper fixed wall bounding nozzle flowpath and at least a portion of the upper triangular surface extending aftwardly of the first and second fixed sidewalls to an apex of the triangular surface.
15. A vectorable nozzle as claimed in claim 14 further comprising the upper pivotable wall including a widthwise aftwardly tapered section.
16. A vectorable nozzle as claimed in claim 15 further comprising the tapered section having an isosceles triangular planform area including side edges extending equi-angularly aftwardly from a base line between the tapered section and a non-tapered section of the upper pivotable wall.
17. A vectorable nozzle as claimed in claim 16 further comprising taper angles between the side edges and the base line and the taper angles sized for allowing the side edges to substantially abut respective ones of the sidewalls when the pivotable ramp structure is pivoted sideways.
18. A vectorable nozzle as claimed in claim 17 further comprising a fin attached to the pivotable ramp structure.
19. A vectorable nozzle as claimed in claim 18 further comprising the fin being attached to the pivotable ramp structure along at least longitudinally extending first and second portions of the lower pivotable wall and the pivotable ramp respectively.
20. A vectorable nozzle as claimed in claim 19 further comprising the fin extending longitudinally over a pivot point where the ramp structure is pivotally connected to the lower fixed wall.
21. A vectorable nozzle as claimed in claim 15 further comprising:
the upper pivotable wall including a widthwise aftwardly tapered section and a base line between the tapered section and a non-tapered section of the upper pivotable wall,
a throat extending substantially downward across the nozzle flowpath from the outer nozzle wall to the ramp structure, and
the tapered and non-tapered sections of the upper pivotable wall being contoured so that the throat extends widthwise substantially along the base line during vectored and unvectored operation of the nozzle.
22. A vectorable nozzle as claimed in claim 21 further comprising the tapered section having an isosceles triangular planform area including side edges extending equi-angularly aftwardly from the base line between the tapered and the non-tapered sections of the upper pivotable wall.
23. A vectorable nozzle as claimed in claim 22 further comprising taper angles between the side edges and the base line and the taper angles sized for allowing the side edges to substantially abut respective ones of the sidewalls when the pivotable ramp structure is pivoted sideways.
24. A vectorable nozzle as claimed in claim 23 further comprising a fin attached to the pivotable ramp structure.
25. A vectorable nozzle as claimed in claim 24 further comprising the fin being attached to the pivotable ramp structure along at least longitudinally extending first and second portions of the lower pivotable wall and the pivotable ramp respectively.
26. A vectorable nozzle as claimed in claim 25 further comprising the fin extending longitudinally over a pivot point where the ramp structure is pivotally connected to the lower fixed wall.
US10/930,881 2004-08-31 2004-08-31 Vectorable nozzle with sideways pivotable ramp Active 2024-11-29 US7055307B2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US10/930,881 US7055307B2 (en) 2004-08-31 2004-08-31 Vectorable nozzle with sideways pivotable ramp
ES05254714T ES2420760T3 (en) 2004-08-31 2005-07-28 Adjustable nozzle with laterally pivoting ramp
EP05254714.8A EP1630399B1 (en) 2004-08-31 2005-07-28 Vectorable nozzle with sideways pivotable ramp

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/930,881 US7055307B2 (en) 2004-08-31 2004-08-31 Vectorable nozzle with sideways pivotable ramp

Publications (2)

Publication Number Publication Date
US20060042230A1 US20060042230A1 (en) 2006-03-02
US7055307B2 true US7055307B2 (en) 2006-06-06

Family

ID=35058552

Family Applications (1)

Application Number Title Priority Date Filing Date
US10/930,881 Active 2024-11-29 US7055307B2 (en) 2004-08-31 2004-08-31 Vectorable nozzle with sideways pivotable ramp

Country Status (3)

Country Link
US (1) US7055307B2 (en)
EP (1) EP1630399B1 (en)
ES (1) ES2420760T3 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080223992A1 (en) * 2007-03-16 2008-09-18 The Boeing Company High-Performance Low-Noise Aircraft Exhaust Systems and Methods
US20090158703A1 (en) * 2007-12-20 2009-06-25 Dale William Petty Sliding ramp nozzle system for a gas turbine engine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7096662B2 (en) * 2004-09-28 2006-08-29 General Electric Company Variable area throat exhaust nozzle with vectorable sideways shifting of exhaust flow
US7475548B2 (en) 2005-09-09 2009-01-13 General Electric Company Vectorable nozzle with pivotable triangular panels
AU2006246449B2 (en) * 2006-11-29 2013-05-02 General Electric Company Vectorable nozzle with pivotable triangular panels
EP1927745B1 (en) * 2006-11-29 2012-08-01 General Electric Company Vectorable nozzle with pivotable triangular panels

Citations (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3096049A (en) * 1960-01-25 1963-07-02 Edward S Karasinski Steering means for space vehicles missiles and high altitude flying craft
US4023105A (en) * 1975-08-25 1977-05-10 Rca Corporation Counter type remote control receiver producing binary outputs correlated with numerical commands of a companion remote control transmitter
US4110972A (en) * 1976-12-16 1978-09-05 United Technologies Corporation Seal means for a movable centerbody in a two dimensional nozzle
US4280660A (en) * 1979-08-17 1981-07-28 General Electric Company Vectorable nozzle
US4641782A (en) * 1981-02-24 1987-02-10 Rolls-Royce Plc Jet propulsion nozzle
US4747543A (en) * 1987-04-14 1988-05-31 United Technologies Corporation Nozzle flap cooling liner
US4801087A (en) * 1986-01-23 1989-01-31 Rolls-Royce Plc Exhaust nozzle for a gas turbine engine
US4848664A (en) * 1987-12-07 1989-07-18 United Technologies Corporation Yaw thrust vectoring exhaust nozzle
US4978071A (en) * 1989-04-11 1990-12-18 General Electric Company Nozzle with thrust vectoring in the yaw direction
US5016818A (en) * 1989-08-21 1991-05-21 General Electric Company Integral transition and convergent section exhaust nozzle
US5050803A (en) * 1989-10-12 1991-09-24 General Electric Company Actuation system for positioning a vectoring exhaust nozzle
US5082181A (en) * 1989-12-18 1992-01-21 The Boeing Company Gas jet engine nozzle
US5092524A (en) 1990-02-12 1992-03-03 Mcdonnell Douglas Corporation Nozzle throat disc for thrust vectoring
US5142862A (en) * 1990-04-09 1992-09-01 The Boeing Company Thrust reversing system for high bypass fan engines
US5261604A (en) * 1992-05-11 1993-11-16 General Electric Company Yaw vectoring blade
US5294055A (en) 1992-09-08 1994-03-15 Mcdonnell Douglas Corporation Rotatable arms for thrust vectoring and changing the area of a nozzle throat
US5335489A (en) * 1993-07-09 1994-08-09 United Technologies Corporation Gas turbine vectoring exhaust nozzle
US5431344A (en) * 1993-11-12 1995-07-11 United Technologies Corporation Sliding throat gas turbine engine nozzle
US5437412A (en) * 1993-06-23 1995-08-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Variable geometry jet engine exhaust nozzle
US5511376A (en) * 1993-08-31 1996-04-30 United Technologies Corporation Axisymmetric vectoring nozzle
US5833139A (en) * 1995-09-06 1998-11-10 United Technologies Corporation Single variable flap exhaust nozzle
US20030145599A1 (en) * 2002-02-01 2003-08-07 Renggli Bernard J. Methods and apparatus for sealing gas turbine engine nozzles
US6857600B1 (en) * 2002-04-26 2005-02-22 General Electric Company Infrared suppressing two dimensional vectorable single expansion ramp nozzle
US6948317B2 (en) * 2003-10-31 2005-09-27 General Electric Company Methods and apparatus for flade engine nozzle

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3040523A (en) * 1958-10-23 1962-06-26 Nathan C Price Variable area propulsive nozzle
GB2292125B (en) * 1981-10-13 1996-07-10 Rolls Royce Nozzle capable of varying the direction of discharge of fluid therefrom

Patent Citations (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3096049A (en) * 1960-01-25 1963-07-02 Edward S Karasinski Steering means for space vehicles missiles and high altitude flying craft
US4023105A (en) * 1975-08-25 1977-05-10 Rca Corporation Counter type remote control receiver producing binary outputs correlated with numerical commands of a companion remote control transmitter
US4110972A (en) * 1976-12-16 1978-09-05 United Technologies Corporation Seal means for a movable centerbody in a two dimensional nozzle
US4280660A (en) * 1979-08-17 1981-07-28 General Electric Company Vectorable nozzle
US4641782A (en) * 1981-02-24 1987-02-10 Rolls-Royce Plc Jet propulsion nozzle
US4801087A (en) * 1986-01-23 1989-01-31 Rolls-Royce Plc Exhaust nozzle for a gas turbine engine
US4747543A (en) * 1987-04-14 1988-05-31 United Technologies Corporation Nozzle flap cooling liner
US4848664A (en) * 1987-12-07 1989-07-18 United Technologies Corporation Yaw thrust vectoring exhaust nozzle
US4978071A (en) * 1989-04-11 1990-12-18 General Electric Company Nozzle with thrust vectoring in the yaw direction
US5016818A (en) * 1989-08-21 1991-05-21 General Electric Company Integral transition and convergent section exhaust nozzle
US5050803A (en) * 1989-10-12 1991-09-24 General Electric Company Actuation system for positioning a vectoring exhaust nozzle
US5082181A (en) * 1989-12-18 1992-01-21 The Boeing Company Gas jet engine nozzle
US5092524A (en) 1990-02-12 1992-03-03 Mcdonnell Douglas Corporation Nozzle throat disc for thrust vectoring
US5142862A (en) * 1990-04-09 1992-09-01 The Boeing Company Thrust reversing system for high bypass fan engines
US5261604A (en) * 1992-05-11 1993-11-16 General Electric Company Yaw vectoring blade
US5294055A (en) 1992-09-08 1994-03-15 Mcdonnell Douglas Corporation Rotatable arms for thrust vectoring and changing the area of a nozzle throat
US5437412A (en) * 1993-06-23 1995-08-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Variable geometry jet engine exhaust nozzle
US5335489A (en) * 1993-07-09 1994-08-09 United Technologies Corporation Gas turbine vectoring exhaust nozzle
US5511376A (en) * 1993-08-31 1996-04-30 United Technologies Corporation Axisymmetric vectoring nozzle
US5431344A (en) * 1993-11-12 1995-07-11 United Technologies Corporation Sliding throat gas turbine engine nozzle
US5833139A (en) * 1995-09-06 1998-11-10 United Technologies Corporation Single variable flap exhaust nozzle
US20030145599A1 (en) * 2002-02-01 2003-08-07 Renggli Bernard J. Methods and apparatus for sealing gas turbine engine nozzles
US6857600B1 (en) * 2002-04-26 2005-02-22 General Electric Company Infrared suppressing two dimensional vectorable single expansion ramp nozzle
US6948317B2 (en) * 2003-10-31 2005-09-27 General Electric Company Methods and apparatus for flade engine nozzle

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080223992A1 (en) * 2007-03-16 2008-09-18 The Boeing Company High-Performance Low-Noise Aircraft Exhaust Systems and Methods
US7726609B2 (en) 2007-03-16 2010-06-01 The Boeing Company High-performance low-noise aircraft exhaust systems and methods
US20090158703A1 (en) * 2007-12-20 2009-06-25 Dale William Petty Sliding ramp nozzle system for a gas turbine engine
US8739548B2 (en) 2007-12-20 2014-06-03 United Technologies Corporation Sliding ramp nozzle system for a gas turbine engine

Also Published As

Publication number Publication date
US20060042230A1 (en) 2006-03-02
EP1630399A3 (en) 2011-09-28
EP1630399B1 (en) 2013-05-22
EP1630399A2 (en) 2006-03-01
ES2420760T3 (en) 2013-08-26

Similar Documents

Publication Publication Date Title
EP1640590B1 (en) Variable area throat exhaust nozzle with vectorable sideways shifting of exhaust flow
US7475548B2 (en) Vectorable nozzle with pivotable triangular panels
EP1206384B1 (en) Supersonic external-compression diffuser and method for designing same
US8371104B2 (en) System and apparatus for vectoring nozzle exhaust plume from a nozzle
US4978071A (en) Nozzle with thrust vectoring in the yaw direction
US8020367B2 (en) Nozzle with yaw vectoring vane
US4280660A (en) Vectorable nozzle
US7628356B2 (en) Yaw control device for a nozzle having a rectangular outlet section
EP3109153B1 (en) Swept gradient boundary layer diverter
US8327617B2 (en) Outlet nozzle for a jet engine, an aircraft comprising the outlet nozzle and a method for controlling a gas flow from the jet engine
US20060150612A1 (en) Thrust vector control
EP1630399B1 (en) Vectorable nozzle with sideways pivotable ramp
US10190539B2 (en) Inlet flow restrictor
WO2010022362A2 (en) Jet engine exhaust nozzle and associated system and method of use
EP4141247B1 (en) Translating cowl thrust reverser system with efflux management
AU2013211514B2 (en) Vectorable nozzle with pivotable triangular panels
EP2659118B1 (en) Flight vehicle, propulsion system and thrust vectoring system
EP1927745B1 (en) Vectorable nozzle with pivotable triangular panels
CA2569179C (en) Vectorable nozzle with pivotable triangular panels
US3976088A (en) Dual side-mounted inlet-vehicle orientation
EP4180332A1 (en) Fuselage for an aircraft with fuselage-integrated tailplane
US11772809B2 (en) Fuselage for an aircraft with fuselage-integrated tailplane

Legal Events

Date Code Title Description
AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:WEHNER, EDWARD JAMES;REEL/FRAME:015762/0631

Effective date: 20040830

FEPP Fee payment procedure

Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

STCF Information on status: patent grant

Free format text: PATENTED CASE

FPAY Fee payment

Year of fee payment: 4

FPAY Fee payment

Year of fee payment: 8

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 12TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1553)

Year of fee payment: 12